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    Unmanned aerial vehicle
    121.
    发明授权
    Unmanned aerial vehicle 有权

    公开(公告)号：US09815554B2

    公开(公告)日：2017-11-14

    申请号：US14858179

    申请日：2015-09-18

    Applicant: Lance Butler Plater

    Inventor： Lance Butler Plater

    IPC: B64C1/00 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/145 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2211/00 ,  B64D2221/00

    Abstract: An unmanned aerial vehicle (UAV) which in some embodiments may comprise a fuselage which includes a cavity formed by an interior cavity wall and a fuselage exterior wall, with the cavity disposed within the fuselage. A first electronic module may be electrically coupled to a first magnetic connector and a second electronic module may be electrically coupled to a second magnetic connector. Electronic communication between the first and second modules may be provided by contact between the first magnetic connector and the second magnetic connector. In further embodiments, when removably positioned adjacent to each other in the cavity, the first magnetic connector may contact the second magnetic connector to establish electronic communication between the first and second modules.

    PNEUMATIC YAW CONTROL EFFECTOR FOR AIRCRAFT
    122.
    发明申请
    PNEUMATIC YAW CONTROL EFFECTOR FOR AIRCRAFT 有权

    公开(公告)号：US20170088253A1

    公开(公告)日：2017-03-30

    申请号：US15052558

    申请日：2016-02-24

    Applicant: David R. Williams ,  Jürgen Seidel

    Inventor： David R. Williams ,  Jürgen Seidel

    IPC: B64C15/14 ,  B64D33/00 ,  B64C39/02

    CPC classification number: B64C15/14 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104 ,  B64D33/00

    Abstract: An apparatus and method for controlling a yaw moment of a flight vehicle, such as an aircraft. A wing structure of the flight vehicle has a first opening or actuator positioned by a first apex section of a first side of the wing, and has a second opening or actuator positioned away from or at a distance from a second apex section of a second side of the wing. The first side and the second side can each be positioned or located opposite a centerline of the wing or wing structure. A pressure source or other pressure supply device is in communication with the first opening or actuator and the second opening or actuator to which a pressurized fluid, such as air, is controlled and delivered to control or vary the yaw moment of the flight vehicle.

    Multi-Role Aircraft With Interchangeable Mission Modules
    123.
    发明申请
    Multi-Role Aircraft With Interchangeable Mission Modules 审中-公开
    具有可互换任务模块的多角色飞机

    公开(公告)号：US20170066532A1

    公开(公告)日：2017-03-09

    申请号：US15352465

    申请日：2016-11-15

    Applicant: Abe Karem

    Inventor： Abe Karem

    IPC: B64C39/10 ,  B64C3/56 ,  B64C39/02 ,  B64C1/06

    CPC classification number: B64C39/10 ,  B64C1/00 ,  B64C1/0009 ,  B64C1/061 ,  B64C1/065 ,  B64C1/26 ,  B64C3/56 ,  B64C25/10 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/126 ,  B64C2211/00 ,  B64D37/00 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/43

    Abstract: A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

    Abstract translation: 飞行可操作的，真正模块化的飞机具有飞行器核心，一个或多个外翼构件，机身，驾驶舱，前后联轴器，尾翼和尾翼部分可在其运行寿命期间可拆卸地联接和/或更换 的飞机。 在优选实施例中，飞机核心容纳推进发动机，航空电子设备，至少80％的燃料和所有起落架。 飞机核心优选地构造有弯曲的前向和后部复合翼梁，其在中心部分处传递载荷，同时容纳中翼构造。 飞机核心优选地具有大的中心空间，其大小可互换地携带军械发射器，监视有效载荷，电子对抗措施和其他类型的货物。 考虑的飞机可能相当大，例如具有至少80英尺的翼展。

    PROPELLER HAVING EXTENDING OUTER BLADE
    124.
    发明申请
    PROPELLER HAVING EXTENDING OUTER BLADE 审中-公开
    螺旋桨有扩展外刀片

    公开(公告)号：US20170029091A1

    公开(公告)日：2017-02-02

    申请号：US14810109

    申请日：2015-07-27

    Applicant: JONATHON J. LINCH ,  KYLE M. RAHRIG

    Inventor： JONATHON J. LINCH ,  KYLE M. RAHRIG

    IPC: B64C11/00 ,  B64C39/02

    CPC classification number: B64C11/001 ,  B64C39/024 ,  B64C39/10 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/165

    Abstract: A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. The ring shroud includes an inner ring surface and a radially spaced, oppositely facing outer ring surface. At least one propeller blade is fixedly attached to both the hub and the inner ring surface and extends radially therebetween for mutual rotation therewith. At least one extending blade has a first extending blade end radially spaced from a second extending blade end. The first extending blade end is fixedly attached to the outer ring surface. The second extending blade end is cantilevered from the first extending blade end and is radially spaced from the ring shroud.

    Abstract translation: 螺旋桨包括同轴地围绕纵向轴线的轮毂。 环形护罩同轴地围绕纵向轴线并与轮毂径向间隔开。 环形护罩包括内环表面和径向间隔开的相对的外环表面。 至少一个螺旋桨叶片固定地附接到轮毂和内环表面并且在其间径向延伸以与其相互旋转。 至少一个延伸叶片具有与第二延伸叶片端部径向间隔开的第一延伸叶片端部。 第一延伸叶片端固定地附接到外环表面。 第二延伸叶片端部从第一延伸叶片端部悬臂并且与环形护罩径向间隔开。

    Aerial System and Vehicle for Continuous Operation
    125.
    发明申请
    Aerial System and Vehicle for Continuous Operation 有权
    空中系统和车辆连续运行

    公开(公告)号：US20170021944A1

    公开(公告)日：2017-01-26

    申请号：US15291878

    申请日：2016-10-12

    Applicant: Aurora Flight Sciences Corporation

    Inventor： James Peverill ,  Adam Woodworth ,  Benjamin Freudberg ,  Dan Cottrell ,  Terrence McKenna

    IPC: B64F1/02 ,  B64C39/02 ,  B64F1/36

    CPC classification number: B64F1/02 ,  B60L11/1816 ,  B60L11/1838 ,  B60L2200/10 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/066 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/182 ,  B64D47/04 ,  B64D47/08 ,  B64F1/362 ,  G05D1/101 ,  G06K9/0063

    Abstract: An aerial vehicle landing station comprising a first post and a second post, wherein the second post is spaced apart from the first post and a cable to capture an aerial vehicle, wherein the cable is stretched between the first post and the second post and configured to support the weight of the aerial vehicle once captured and the cable may provide a charging current to the aerial vehicle once captured. One or more markers may be further positioned on the cable to designate a landing point, wherein the one or more markers are configured to be visually tracked by the aerial vehicle. A cable management device coupled to the cable via one or more pulleys may regulate tension of the cable. A communications transceiver at the aerial vehicle landing station may wirelessly communicate data with the aerial vehicle.

    Abstract translation: 一种包括第一柱和第二柱的飞行器着陆台，其中所述第二柱与所述第一柱分开并且用于捕获空中飞行器的缆线，其中所述缆线在所述第一柱和所述第二柱之间被拉伸，并且被配置为 一旦捕获，支持飞行器的重量，并且电缆可以在捕获后向飞行器提供充电电流。 可以将一个或多个标记物进一步定位在电缆上以指定着陆点，其中所述一个或多个标记被配置为由飞行器视觉上跟踪。 经由一个或多个滑轮联接到电缆的电缆管理装置可以调节电缆的张力。 航空器着陆站的通信收发器可以与飞行器无线地传送数据。

    Multi-role unmanned vehicle system and associated methods
    130.
    发明授权
    Multi-role unmanned vehicle system and associated methods 有权
    多角色无人驾驶车辆系统及相关方法

    公开(公告)号：US09096106B2

    公开(公告)日：2015-08-04

    申请号：US13470866

    申请日：2012-05-14

    Applicant: Bruce Hanson ,  Mark Everly

    Inventor： Bruce Hanson ,  Mark Everly

    IPC: G01C22/00 ,  G05D1/00 ,  B60F5/00 ,  B63B1/04 ,  B63G8/00 ,  B63B35/00 ,  B64C35/00 ,  B64C39/02 ,  B63B1/32 ,  B63G8/22 ,  B63G8/26 ,  B63B1/20

    CPC classification number: B60F5/00 ,  B63B1/042 ,  B63B1/322 ,  B63B2001/206 ,  B63B2035/006 ,  B63B2035/007 ,  B63G8/22 ,  B63G8/26 ,  B63G2008/002 ,  B63G2008/004 ,  B64C35/00 ,  B64C39/024 ,  B64C2201/028 ,  Y02T70/12

    Abstract: An unmanned vehicle may include a vehicle body that comprises an enclosed hull. The unmanned vehicle may include a propulsion, a ballast control system, a center of gravity system, a pressurization system, a control surface system, a navigation control system, and an on board master control system. The on board master control system may execute local control over operation of the various systems of the unmanned vehicle. The unmanned vehicle may also include a power supply carried by a portion of the vehicle body to provide power to the various systems. The various systems of the unmanned vehicle may be independently operable to support selective operation of the unmanned vehicle in the air, on the surface of the water, and below the surface of the water.

    Abstract translation: 无人驾驶车辆可以包括包括封闭船体的车体。 无人驾驶车辆可以包括推进，镇流器控制系统，重心系统，加压系统，控制面系统，导航控制系统和车载主控制系统。 车载主控制系统可以执行对无人驾驶车辆的各种系统的操作的本地控制。 无人驾驶车辆还可以包括由车身的一部分承载的电力供应给各种系统。 无人驾驶车辆的各种系统可以独立地可操作以支持无人驾驶车辆在空气中，水面上以及水面以下的选择性操作。

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